Aerothermal performance analysis and knowledge discovery of film holes on the squealer tip of a gas turbine blade

Author:

Li Chenxi

Funder

China Postdoctoral Science Foundation

Natural Science Basic Research Program of Shaanxi Province

Publisher

Elsevier BV

Subject

General Engineering,Condensed Matter Physics

Reference28 articles.

1. Cavity heat transfer on a transverse grooved wall in a narrow flow channel;Metzger;ASME J. Heat Transfer,1989

2. Heat Transfer Coefficient and Film-Cooling Effectiveness on a Gas Turbine Blade Tip;Kwak,2002

3. Film-cooling effectiveness on a gas turbine blade tip using pressure-sensitive paint;Ahn;ASME J. Heat Transfer,2005

4. Numerical Prediction of Film Cooling and Heat Transfer on the Leading Edge of a Rotating Blade with Two Rows Holes in a 1-1/2 Turbine Stage at Design and off Design Conditions;Yang,2005

5. Film-cooling prediction on turbine blade tip with various film hole configurations;Yang;J. Thermophys. Heat Tran.,2006

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